EP2206884B1 - Rotor cooling circuit - Google Patents

Rotor cooling circuit Download PDF

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Publication number
EP2206884B1
EP2206884B1 EP09180591.1A EP09180591A EP2206884B1 EP 2206884 B1 EP2206884 B1 EP 2206884B1 EP 09180591 A EP09180591 A EP 09180591A EP 2206884 B1 EP2206884 B1 EP 2206884B1
Authority
EP
European Patent Office
Prior art keywords
cooling
rotor
compressor
path
cooled
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP09180591.1A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2206884A3 (en
EP2206884A2 (en
Inventor
Tushar S. Desai
Roger Clayton Walker
Richard Francis Gutta
Fernando J Casanova
Ravi Meenaks
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2206884A2 publication Critical patent/EP2206884A2/en
Publication of EP2206884A3 publication Critical patent/EP2206884A3/en
Application granted granted Critical
Publication of EP2206884B1 publication Critical patent/EP2206884B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Definitions

  • the present invention relates to rotor cooling and, more particularly, to a rotor cooling circuit including combined compressor cooling and turbine cooling to thereby increase efficiency and total power output.
  • the unit rotor In a gas turbine, the unit rotor during its full load operation experiences temperatures higher than the material capability. As such, the rotor components are subject to low cycle fatigue (LCF), embrittlement and creep issues, which are detrimental to the performance of the system.
  • the unit rotor wheels require a positive purge system to cool the wheels during full load operation. The rotor purge also maintains uniform wheel temperatures during startup and shutdown to achieve good wheel to wheel behavior.
  • the unit rotor receives cooled cooling air (CCA) through the compressor discharge casing (CDC) and the inner barrel.
  • CCA cooled cooling air
  • CDC compressor discharge casing
  • the cooling flow is split at the bore section forward for the compressor rotor cooling and aft for the turbine rotor cooling.
  • the amount of flow going to each circuit is controlled at the flange or the rabbet joints through design features such as metering slots. See FIG. 1 .
  • This cooling scheme uses an excess amount of CCA, which impacts the overall efficiency of the machine and the final power output. Additionally, the greater amount of cooling flow requires a larger size heat exchanger, which also results in an efficiency loss in the overall scheme of the system.
  • a cooling circuit for cooling a rotor having a compressor rotor and a turbine rotor according to claim 1.
  • a method of cooling a rotor includes the steps of directing cooled cooling air along a first cooling path defined through openings in rotor wheels of the compressor rotor, according to claim 4.
  • a cooling circuit includes a first cooling path through the compressor rotor in series with a second cooling path through the turbine rotor such that one amount of cooling air is used for cooling both the compressor rotor and the turbine rotor.
  • FIG. 2 is a cross sectional view of a gas turbine including the cooling circuit of the described embodiment.
  • a unit rotor in the gas turbine includes a compressor rotor 12 and a turbine rotor 14.
  • the cooling circuit includes a source of cooled cooling air 16, which is routed through the compressor discharge casing (CDC) via a heat exchanger upstream of the unit rotor.
  • CDC compressor discharge casing
  • the cooling circuit includes a first cooling path 18 defined through openings in rotor wheels 20 of the compressor rotor 12.
  • the first cooling path 18 directs the cooled cooling air across the rotor wheels 20 and into a bore section 22 of the compressor rotor 12.
  • a second cooling path 24 is defined in series with the first cooling path 18.
  • the second cooling path 24 directs the cooled cooling air across rotor wheels 20 of the turbine rotor 14.
  • a small amount of compressor discharge flow (to be used for rotor cooling) is routed to the rotor through the CDC extraction port to the heat exchanger skid and cooled. This flow is used as the cooled cooling air (CCA) and used for rotor cooling. The heat extracted from this cooling flow in the heat exchanger is used to improve the efficiency of the steam turbine.
  • CCA cooled cooling air
  • the cooling flow in the first cooling path 18 is directed through a plurality of axial holes in the inertia belt 25 for compressor rotor cooling.
  • the inertia belt includes twenty-four axial holes.
  • the remaining CCA flow is directed across the high pressure packing (HPP) brush seal 26, bypass holes across the HPP seals, and the stage-18 compressor aft rim.
  • the cooling flow in the compressor rotor inertia belt 25 is split at the compressor flanges for rim cooling, bore cooling and forward stage cooling using metering circuits or the like.
  • High performance impellers 27 in the bore sections of the compressor wheels help maintain the flow pressure and swirl the flow to rotor speed. Flow from the compressor stages is collected and combined at the centerline of the unit-rotor in the bore section 22 and channeled aft toward the second cooling path 24 for cooling the turbine rotor 14.
  • the compressor stages 13 and 15 are converted to solid bores and cooled through individual parallel flow path cooling circuits.
  • the CCA system has a bypass around the heat exchanger (controlled by valves or the like) during the startup to achieve better wheel to wheel behavior and improved LCF and fracture life in the rotor wheels.
  • Combining the cooling flow circuits into first and second series cooling circuits serves to increase the overall efficiency of the system and to reduce the heat exchanger size.
  • the combined rotor cooling flow thus performs double duty by first cooling the compressor rotor and using the same flow to cool the turbine rotor.
  • the new cooling scheme maintains the external control of the system and reduces the total amount of CCA required for rotor cooling by 35%.
  • the design not only reduces the cost of the heat exchanger skid, but as determined by theoretical calculation improves the net combined efficiency of the system by 0.138%.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09180591.1A 2009-01-09 2009-12-23 Rotor cooling circuit Not-in-force EP2206884B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/351,408 US7993102B2 (en) 2009-01-09 2009-01-09 Rotor cooling circuit

Publications (3)

Publication Number Publication Date
EP2206884A2 EP2206884A2 (en) 2010-07-14
EP2206884A3 EP2206884A3 (en) 2014-01-01
EP2206884B1 true EP2206884B1 (en) 2015-02-25

Family

ID=42077846

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09180591.1A Not-in-force EP2206884B1 (en) 2009-01-09 2009-12-23 Rotor cooling circuit

Country Status (4)

Country Link
US (1) US7993102B2 (enrdf_load_stackoverflow)
EP (1) EP2206884B1 (enrdf_load_stackoverflow)
JP (1) JP5253425B2 (enrdf_load_stackoverflow)
CN (1) CN101943167B (enrdf_load_stackoverflow)

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* Cited by examiner, † Cited by third party
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US8186933B2 (en) * 2009-03-24 2012-05-29 General Electric Company Systems, methods, and apparatus for passive purge flow control in a turbine
US8807941B2 (en) * 2011-02-03 2014-08-19 General Electric Company Cross-over purge flow system for a turbomachine wheel member
US8961132B2 (en) 2011-10-28 2015-02-24 United Technologies Corporation Secondary flow arrangement for slotted rotor
US9068507B2 (en) 2011-11-16 2015-06-30 General Electric Company Compressor having purge circuit and method of purging
US9085983B2 (en) 2012-03-29 2015-07-21 General Electric Company Apparatus and method for purging a gas turbine rotor
US9188010B2 (en) * 2012-06-25 2015-11-17 General Electric Company Systems and methods to control flow in a rotor wheel
US20170002834A1 (en) * 2013-07-15 2017-01-05 United Technologies Corporation Cooled compressor
US9528377B2 (en) 2013-08-21 2016-12-27 General Electric Company Method and system for cooling rotor blade angelwings
EP2868865A1 (de) * 2013-10-31 2015-05-06 Siemens Aktiengesellschaft Gasturbine sowie Verfahren zu deren Kühlung
US9719425B2 (en) 2014-05-23 2017-08-01 General Electric Company Cooling supply circuit for turbomachinery
EP2995769B1 (en) * 2014-09-12 2019-11-13 United Technologies Corporation Thermal regulation of a turbomachine rotor
US10837288B2 (en) 2014-09-17 2020-11-17 Raytheon Technologies Corporation Secondary flowpath system for a gas turbine engine
US10107206B2 (en) * 2014-11-05 2018-10-23 United Technologies Corporation High pressure compressor rotor thermal conditioning using discharge pressure air
US10612383B2 (en) 2016-01-27 2020-04-07 General Electric Company Compressor aft rotor rim cooling for high OPR (T3) engine
EP3342979B1 (en) 2016-12-30 2020-06-17 Ansaldo Energia Switzerland AG Gas turbine comprising cooled rotor disks
US10641174B2 (en) 2017-01-18 2020-05-05 General Electric Company Rotor shaft cooling
US10907545B2 (en) 2017-06-27 2021-02-02 General Electric Company Cooling system for a turbine engine
US11060530B2 (en) 2018-01-04 2021-07-13 General Electric Company Compressor cooling in a gas turbine engine
US10746098B2 (en) 2018-03-09 2020-08-18 General Electric Company Compressor rotor cooling apparatus
US10982546B2 (en) 2018-09-19 2021-04-20 General Electric Company Flow-diverting systems for gas turbine air separator
CN109736905A (zh) * 2019-03-21 2019-05-10 上海电气电站设备有限公司 汽轮机多级汽缸间联合冷却系统
US11525400B2 (en) 2020-07-08 2022-12-13 General Electric Company System for rotor assembly thermal gradient reduction
US11674396B2 (en) 2021-07-30 2023-06-13 General Electric Company Cooling air delivery assembly
US12320299B2 (en) 2022-07-20 2025-06-03 General Electric Company Cooling air delivery system and methods thereof
US12044172B2 (en) 2022-11-02 2024-07-23 General Electric Company Air guide for a gas turbine engine

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Also Published As

Publication number Publication date
EP2206884A3 (en) 2014-01-01
US20100178168A1 (en) 2010-07-15
CN101943167A (zh) 2011-01-12
EP2206884A2 (en) 2010-07-14
JP2010159760A (ja) 2010-07-22
US7993102B2 (en) 2011-08-09
JP5253425B2 (ja) 2013-07-31
CN101943167B (zh) 2015-02-11

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